# Oblique + Normal Compression shock and nose cone angles

Hi there.
I'm using the following equations as part of my physics research paper:
http://www.grc.nasa.gov/WWW/K-12/airplane/normal.html
The initial equation, concerning the half angle of the nose cone of the object, gives me a rather trivial answer at mach 1.5..
a > 0.199 (3sf)
Now, anything over 0.199 degrees gives a normal shock right? But anything below gives an oblique shock.
What are the normal nose cone angles for supersonic combat aircraft?? Are they below or above this? If above, does this mean Supersonic aircraft experience a normal shock at the nose? But an oblique shock at the knife edge wings?